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Title: Variable volume combustor with aerodynamic support struts

Abstract

The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and providing the flow of fuel therethrough. The support struts may include an aerodynamic contoured shape so as to distribute evenly a flow of air to the micro-mixer fuel nozzles.

Inventors:
; ; ;
Publication Date:
Research Org.:
GENERAL ELECTRIC COMPANY, Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1346054
Patent Number(s):
9,587,562
Application Number:
13/760,097
Assignee:
GENERAL ELECTRIC COMPANY NETL
DOE Contract Number:
FC26-05NT42643
Resource Type:
Patent
Resource Relation:
Patent File Date: 2013 Feb 06
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Ostebee, Heath Michael, Johnson, Thomas Edward, Stewart, Jason Thurman, and Keener, Christopher Paul. Variable volume combustor with aerodynamic support struts. United States: N. p., 2017. Web.
Ostebee, Heath Michael, Johnson, Thomas Edward, Stewart, Jason Thurman, & Keener, Christopher Paul. Variable volume combustor with aerodynamic support struts. United States.
Ostebee, Heath Michael, Johnson, Thomas Edward, Stewart, Jason Thurman, and Keener, Christopher Paul. Tue . "Variable volume combustor with aerodynamic support struts". United States. doi:. https://www.osti.gov/servlets/purl/1346054.
@article{osti_1346054,
title = {Variable volume combustor with aerodynamic support struts},
author = {Ostebee, Heath Michael and Johnson, Thomas Edward and Stewart, Jason Thurman and Keener, Christopher Paul},
abstractNote = {The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and providing the flow of fuel therethrough. The support struts may include an aerodynamic contoured shape so as to distribute evenly a flow of air to the micro-mixer fuel nozzles.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Mar 07 00:00:00 EST 2017},
month = {Tue Mar 07 00:00:00 EST 2017}
}

Patent:

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  • The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and for providing the flow of fuel therethrough. The fuel injection system also may include a number of aerodynamic fuel flanges connecting the micro-mixer fuel nozzles and the support struts.
  • The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a conical liner support supporting the liner.
  • The present application and the resultant patent provide a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a center hub for providing the flow of fuel therethrough. The center hub may include a first supply circuit for a first micro-mixer fuel nozzle and a second supply circuit for a second micro-mixer fuel nozzle.
  • The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles, a pre-nozzle fuel injection system supporting the fuel nozzles, and a linear actuator to maneuver the fuel nozzles and the pre-nozzle fuel injection system.
  • The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles, a fuel manifold system in communication with the micro-mixer fuel nozzles to deliver a flow of fuel thereto, and a linear actuator to maneuver the micro-mixer fuel nozzles and the fuel manifold system.